Method of dimensioning and producing stiffened structural components, use of structural condition sensors and an aircraft

• US 7,913,568 B2
• Filed: 12/15/2006
• Issued: 03/29/2011
• Est. Priority Date: 12/29/2005
• Status: Expired due to Fees

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Schmidt, Hans-Jürgen, Telgkamp, Jens
• Primary Examiner(s): Noori; Max
• Application Number:
  US12/094,841
• Publication Number:
  US 20090090813A1
• Time in Patent Office: 1,565 Days
• Field of Search: 737/60, 738/02, 738/08
• US Class Current: 73/760
• CPC Class Codes: B64C 1/068 Fuselage sections
• CPC Class Codes: B64C 2001/0081 from metallic materials
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

The invention concerns a method of dimensioning and producing stiffened structural components (4) comprising at least one shell component (6) and at least one stiffening component (8) which can be connected thereto, in which the shell component (6) and the at least one stiffening component (8) is dimensioned on the assumption of intactness of the at least one stiffening component and having regard to a predetermined safety factor and/or a predetermined structural inspection interval in which a predetermined maximum crack progression in the shell component is not to be exceeded and/or the strength of the structural component is not to fall below a predetermined minimum residual strength, and in which the at least one stiffening element (8) of the structural component dimensioned by this method is equipped with at least one structural condition sensor (30) for detecting intactness; as well as the use of structural condition sensors in an aircraft, in particular a passenger aircraft.

Claims

1. A method of dimensioning and producing stiffened structural components having at least one shell component and at least one stiffening component, the method comprising:

dimensioning the at least one shell component and the at least one stiffening component based upon at least one of (1) a predetermined safety factor and (2) a structural inspection interval in which a predetermined maximum crack progression in the shell component is not to be exceeded and the strength of the structural component does not fall below a predetermined minimum residual strength, the dimensioning also based upon the assumption of intactness of the at least one stiffening component; and

securing the at least one stiffening component to the shell component to form the stiffened structural component,

the at least one stiffening component having a long dimension along the at least one shell component and at least one elongated structural sensor positioned mid-height on the at least one stiffening component, the elongated structural condition sensor extending substantially along the long dimension of the stiffening component and detecting intactness of the stiffened structural components.

2. A method according to claim 1 wherein the method further includes at least one step selected from the group consisting of:

a. determining the stress values acting on the structural component,

b. establishing fixing positions of the stiffening components connected to the shell component,

c. establishing the number of the stiffening components connected to the shell component,

d. establishing material strengths of the shell component and the at least one stiffening component,

e. calculating a progression of a crack occurring in the shell component based upon at least one selected from the group consisting of the stress values;

the predetermined inspection interval;

the number and fixing positions of the stiffening components;

the material strengths of the shell component; and

the material strengths of the stiffening components,

f. calculating a required structural inspection interval as the quotient of the interval between the times of a safely inspectable crack length and a critical crack length and the established safety factor,

g. altering at least one selected from the group consisting of;

the material strengths, the fixing positions of the stiffening components, and the number of the stiffening components of the structural component for adapting the required structural inspection interval to the predetermined inspection interval,

h. producing the structural component by connecting the stiffening components dimensioned in accordance with the foregoing steps, to the shell component, by means of at least one selected from the group consisting;

of riveted connections, welded connections, adhesive connections, laminated connections, and screw connections, and

i. equipping the at least one stiffening component with at least one structural condition sensor.

3. A method according to claim 1 further comprising

calculating a required structural inspection interval as the quotient of the duration until a critical residual strength is reached and the established safety factor.

4. A method according to claim 1 in which the structural component is used in aircraft.

5. A method according to claim 1 in which the structural component is used in passenger aircraft.

6. A method according to claim 5 in which the shell component is used as at least part of an outer skin of a passenger aircraft.

7. A method according to claim 6 in which the at least one stiffening component is a longitudinal stiffener of the outer skin of a passenger aircraft.

8. A method according to claim 6 in which the at least one stiffening component is a transverse stiffener of the outer skin of a passenger aircraft.

9. A method according to claim 1 in which the structural condition sensors are at least one selected from the group consisting of:

electrical tearing wires, vacuum sensors, and optical fibres.

10. A method according to claim 1 in which a plurality of structural condition sensors are arranged at different locations of the at least one stiffening component such that the stiffening component is monitored substantially along its entire length.

11. A method according to claim 1 in which the structural condition sensors are connected to at least one selected from the group consisting of:

means for recording the conditions of the stiffening component, means for assessing the conditions of the stiffening components, and means transmitting the conditions of the stiffening components.

12. A method according to claim 11 in which the means for recording, means for assessing, and means for transmitting the conditions of the stiffening components are one or more data-processing apparatuses.

13. A method according to claim 12 in which the data-processing apparatuses in the event of detection of the defect of one or more stiffening components store said defect in the form of data on a data carrier.

14. A method according to claim 13 further comprising notifying at least one of the aircraft crew and ground staff about the defect by outputting the data with an output means.

15. A method according to claim 14 wherein the at least one of the crew of the aircraft and ground staff is informed immediately after the occurrence of the defect.

19. A method according to claim 1 wherein the at least one elongated structural condition sensor includes a plurality of elongated structural condition sensors substantially parallel to one another at different heights on a side surface of the at least one stiffening component and extending substantially along the long dimension of the at least one stiffening component.

20. A method according to claim 12 wherein the one or more data-processing apparatuses are avionic apparatuses.

21. A method according to claim 12 wherein the data-processing apparatuses transmit data to a further data-processing apparatus in the event of detection of a defect of one or more stiffening components.

16. A method for detecting the intactness of one or more stiffening components of a structural component comprising:

providing a structural component having at least one shell component and at least one stiffening component connected to the at least one shell component, the structural component dimensioned such that at least one condition is met from the group consisting of;

a predetermined maximum crack progression in the shell component is not exceeded and the strength of the structural component does not fall below a predetermined minimum residual strength within a predetermined structural inspection interval; and

detecting the intactness of the at least one stiffening component using at least one elongated structural condition sensor, the at least one stiffening component having a long dimension along the at least one shell component, the at least one elongated structural condition sensor positioned mid-height on the at least one stiffening component and extending substantially along the long dimension of the stiffening component.

22. A method according to claim 16 wherein the at least one elongated structural condition sensor includes a plurality of elongated condition sensors substantially parallel to one another at different heights on a side surface of the at least one stiffening component and extending substantially along the long dimension of the at least one stiffening component.

17. An aircraft comprising:

at least one stiffened structural component having at least one shell component and at least one stiffening component, the at least one shell component and the at least one stiffening component being dimensioned based upon at least one selected from the group consisting of;

(1) a predetermined safety factor and (2) a predetermined structural inspection interval in which a predetermined maximum crack progression in the shell component is not to be exceeded and the strength of the structural component is not to fall below a predetermined minimum residual strength, the at least one structural component also being dimensioned on an assumption of intactness of the at least one stiffening component, the stiffening component having a long dimension along the at least one shell component; and

at least one elongated structural condition sensor positioned mid-height on the at least one stiffening component and extending substantially along the long dimension of the stiffening component the at least one elongated structural condition sensor detecting intactness of the stiffened structural component.

18. An aircraft according to claim 17 wherein the at least one elongated structural condition sensor includes a plurality of structural condition sensors substantially parallel to one another at different heights on a side surface of the at least one stiffening component and extending substantially along the long dimension of the at least one stiffening component.